The need for rudder to coordinate a turn is directly dependent on Angle of Attack (AOA). At positive angles of attack, the down aileron is more in the relative wind than the Up aileron (due to blanking by the wing in front of the aileron). An aircraft that is at zero AOA, (like a fighter unloaded, in a zero-G ballistic arc) requires no rudder. To avoid this problem, in modern aircraft, like the F-15, for example, differential stabilator is used to mitigate this issue. The stick is mechanized so that the further aft it is, the more any lateral motion is directed to generating asymmetrical stabilator deflection, rather than aileron deflection. SO, at high AOA (assuming that stick position is an accurate indicator of AOA), when the pilot moves the stick to the side, the ailerons deflect very little or not at all, but the stabilators at the tail deflect asymmetrically.
The F-16 flight control surfaces are completely computer controlled, so pilot inputs are interpreted as commands for aircraft movement. The computer then determines, based on all known factors (AOA, Airspeed, etc.) what to do with all control surfaces (including the leading and trailing edge flaps) to get the airframe to move in the manner commanded by the flight control inputs.
I never flew the F-16, (perhaps someone who did can clarify), but my guess is that there is no need to depress the rudder pedal in the F-16 to coordinate a turn - that the computer automatically determines how much rudder, or differential stabilator, should be deflected to coordinate the requested roll rate.